The Weight Minimization of a UAV Wing Component Through Structural Optimization

This study focuses on the structural optimization of a composite wing element for an unmanned aerial vehicle. The finite element method is utilized for sizing, and analysis parameters are chosen to obtain accurate results with a minimum simulation time. Acceleration loads are imposed on the model in combination with pressure loads, which are extracted from CFD simulations. At the optimization stage, the thickness and orientation of each critical layer are described as design variables. The main goal is weight minimization, considering both the strength and the stiffness of the structure. Strength is described by the failure index parameter and stiffness is described by critical deflections, which affect the aerodynamic performance of the vehicle. Results include thickness and failure index distribution over the surfaces, as well as the overall deflection of the structure.